EP1942249A2 - Wärmeübertragungssystem für Turbinenmotoren mit Wärmerohren - Google Patents

Wärmeübertragungssystem für Turbinenmotoren mit Wärmerohren Download PDF

Info

Publication number
EP1942249A2
EP1942249A2 EP07123431A EP07123431A EP1942249A2 EP 1942249 A2 EP1942249 A2 EP 1942249A2 EP 07123431 A EP07123431 A EP 07123431A EP 07123431 A EP07123431 A EP 07123431A EP 1942249 A2 EP1942249 A2 EP 1942249A2
Authority
EP
European Patent Office
Prior art keywords
heat
transfer system
heat transfer
heat pipe
cowling
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP07123431A
Other languages
English (en)
French (fr)
Other versions
EP1942249A3 (de
EP1942249B1 (de
Inventor
Justin P. Stephenson
Thomas Ory Moniz
Kattalaicheri Srinivasan Venkatamarani
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
General Electric Co
Original Assignee
General Electric Co
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by General Electric Co filed Critical General Electric Co
Publication of EP1942249A2 publication Critical patent/EP1942249A2/de
Publication of EP1942249A3 publication Critical patent/EP1942249A3/de
Application granted granted Critical
Publication of EP1942249B1 publication Critical patent/EP1942249B1/de
Expired - Fee Related legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Images

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/04—Blade-carrying members, e.g. rotors for radial-flow machines or engines
    • F01D5/043—Blade-carrying members, e.g. rotors for radial-flow machines or engines of the axial inlet- radial outlet, or vice versa, type
    • F01D5/046—Heating, heat insulation or cooling means
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/02—De-icing means for engines having icing phenomena
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/08—Cooling; Heating; Heat-insulation
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/08—Cooling; Heating; Heat-insulation
    • F01D25/10—Heating, e.g. warming-up before starting
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/08—Heating, heat-insulating or cooling means
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
    • F02C7/047—Heating to prevent icing
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F28—HEAT EXCHANGE IN GENERAL
    • F28D—HEAT-EXCHANGE APPARATUS, NOT PROVIDED FOR IN ANOTHER SUBCLASS, IN WHICH THE HEAT-EXCHANGE MEDIA DO NOT COME INTO DIRECT CONTACT
    • F28D15/00—Heat-exchange apparatus with the intermediate heat-transfer medium in closed tubes passing into or through the conduit walls ; Heat-exchange apparatus employing intermediate heat-transfer medium or bodies
    • F28D15/02—Heat-exchange apparatus with the intermediate heat-transfer medium in closed tubes passing into or through the conduit walls ; Heat-exchange apparatus employing intermediate heat-transfer medium or bodies in which the medium condenses and evaporates, e.g. heat pipes
    • F28D15/0275—Arrangements for coupling heat-pipes together or with other structures, e.g. with base blocks; Heat pipe cores
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/208—Heat transfer, e.g. cooling using heat pipes
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F28—HEAT EXCHANGE IN GENERAL
    • F28F—DETAILS OF HEAT-EXCHANGE AND HEAT-TRANSFER APPARATUS, OF GENERAL APPLICATION
    • F28F2265/00—Safety or protection arrangements; Arrangements for preventing malfunction
    • F28F2265/30—Safety or protection arrangements; Arrangements for preventing malfunction for preventing vibrations
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

  • This invention relates generally to turbine engines, and more particularly to a system and method using heat pipes for transferring heat within a gas turbine engine.
  • IGV splitter nose and booster inlet guide vane
  • exposed components such as the splitter nose and booster inlet guide vane (IGV) leading edges can accumulate ice during operation. Ice accumulation within the engine and over exposed engine structures may be significant. The accreted ice may partially block the fan flowpath and render the fan unstable. The accumulated ice can also be suddenly shed, for example through continued operation of the engine, a throttle burst from lower power operation to higher power operation, or vibrations due to either turbulence or asymmetry of ice accretion.
  • IGV splitter nose and booster inlet guide vane
  • a heat transfer system for a turbine engine including at least one heat pipe having at least a section thereof disposed in contact with an inner surface of a cowling structure.
  • the heat pipe is thermally coupled to a heat source, such that heat from the heat source can be transferred through the heat pipe to the cowling structure.
  • the invention provides a heat transfer system for a turbine engine including an annular cowling structure with a nose portion having an arcuate cross-section.
  • the heat transfer system includes at least one heat pipe having at least a section thereof disposed in contact with an inner surface of the cowling structure.
  • the heat pipe is secured by a mounting structure including a damping element adapted to isolate the heat pipe from vibrations; wherein the heat pipe is thermally coupled to a heat source, such that heat from the heat source can be transferred through the heat pipe to the cowling structure.
  • a gas turbine engine includes: an annular cowling structure with a nose portion having an arcuate cross-section; a plurality of heat pipes, at least a section of each heat pipe being disposed against an inner surface of the cowling structure, the heat pipe secured by a mounting structure including a damping element adapted to isolate the heat pipe from vibrations; and a heat source thermally coupled to the heat pipes such that heat from the heat source can be transferred through the heat pipes to the cowling structure.
  • Figure 1 illustrates a portion of a fan section of a gas turbine engine, including an inner housing 10 with a forward-facing splitter 12, an annular fan casing 14, which is connected to the inner housing 10 by an array of radially extending fan struts 16, and a core inner flowpath 18.
  • the splitter 12 is an annular structure that separates the fan bypass air flow path, indicated generally at "F”, and the core engine air flow path, indicated generally at "C”.
  • a plurality of inlet guide vanes (IGVs) 20 extend between the splitter 12 and the core inner flowpath 18.
  • cowling structure refers generally to any static annular engine structure with a nose portion having an arcuate cross-section
  • annular booster casing 22 forms the radially inner surface of the splitter 12 and serves to contain the rotating booster blades (not shown).
  • the present invention may also be used in configurations in which the splitter 12 is made up of more or fewer components.
  • a plurality of heat pipes 28 are mounted around the booster casing 22. Each heat pipe 28 includes an aft section 30, and a forward section 32, with a transition section 33 therebetween.
  • heat pipes 28 when used in relation to the heat pipes 28, describe the positioning of the heat pipes 28 in areas of relatively high or low temperature, and are not related to any particular aspect of the structure of the heat pipes 28 themselves.
  • the forward sections 32 of the heat pipes 28 are disposed within the splitter nose 26 in a circumferential array.
  • Each forward section 32 is generally arc-shaped to follow the curve of the booster casing 22 and extends in a generally circumferential direction.
  • Each of the forward sections 32 is mounted in the splitter nose 26 so as to achieve good thermal conductivity with the flowpath surface while avoiding vibration and cracking.
  • the forward section 32 is held against the interior surface of the splitter lip 24 by one or more curved, resilient spring clips 42 which are welded, bolted, riveted, or otherwise attached to the booster casing 22.
  • a damping member 44 which may have thermal insulation properties, may be carried by the clip 42 or disposed between the clip 42 and the forward section 32.
  • a suitable material for the damping member 44 is high-temperature silicone.
  • a thermally conductive thermal paste such as silicone paste of a known type, may be disposed between the forward section 32 and the inner surface 46 of the splitter lip 24 to enhance and direct heatflow to the front. Additional thermal insulation (not shown) may be placed inside the splitter lip 24 to cover the back side of the forward section 32 and minimize heat loss.
  • forward sections 132 of heat pipes are held against the inner surface of the splitter lip 24 by one or more brackets 48 which are attached to the splitter lip 24, for example with bolts 50 as shown.
  • a damping member 52 which may have thermal insulation properties, may be disposed between the bracket 48 and the forward section 132.
  • An example of a suitable material for the damping member 52 is high-temperature silicone.
  • a thermally conductive thermal paste such as silicone paste of a known type, may be disposed between the forward section 132 and the inner surface of the splitter lip 24 to enhance and direct heatflow to the front. Additional thermal insulation (not shown) may be placed inside the splitter lip 24 to cover the back side of the forward section 132 and minimize heat loss.
  • forward sections 232 of heat pipes are held against the inner surface of the splitter lip 24 by one or more relatively thin brackets 54 (e.g. sheetmetal) which are captured inside the splitter lip 24.
  • a damping member 56 which may have thermal insulation properties, may be disposed between the bracket 54 and the forward section 232.
  • An example of a suitable material for the damping member 56 is high-temperature silicone.
  • a thermally conductive thermal paste such as silicone paste of a known type, may be disposed between the forward section 232 and the inner surface of the splitter lip 24 to enhance and direct heatflow to the front. Additional thermal insulation (not shown) may be placed inside the splitter lip 24 to cover the back side of the forward section 232 and minimize heat loss.
  • the transition section 33 extends generally axially and interconnects the aft section 30 and the forward section 32. It size and shape depends on the positioning of the associated forward section 32, but most of the transition sections 33 will extend in a circumferential direction to some extent.
  • the aft sections 30 of the heat pipes 28 are generally circumferentially extending. They extend to a heat exchanger (not shown) mounted in a convenient location.
  • the heat exchanger may simply be a housing with an open interior. Oil from the engine's lubrication system enters the heat exchanger through appropriate piping, transfers heat to the heat pipes 28, and then flows back to the engine's lubrication system through a supply line.
  • the oil storage, circulation, and distribution system connected to the heat exchanger is conventional within the gas turbine engine art, and not discussed here. If desired, the heat exchanger could be connected to another type of heat source, such as a bleed air line, an electric source, or another fluid system within the engine.
  • the portion of the heat pipes 28 that lie inside the splitter nose 26 may be formed into oval, flatted, or other non-circular cross-sectional shapes to accommodate a desired cross-sectional area while improving volumetric packaging or heat transfer.
  • Figures 4 and 5 illustrate heat pipes having generally oval cross-sections.
  • Each heat pipe 28 has an elongated outer wall with closed ends which together define a cavity.
  • the cavity is lined with a capillary structure or wick (not shown) and holds a working fluid.
  • working fluids such as gases, water, organic substances, and low-melting point metals are known for use in heat pipes.
  • the working fluid may be non-flammable so as to avoid introducing a fire hazard into the area of the fan casing 10 in the event of a leak or break in the heat pipe 28.
  • the heat pipes 28 are highly efficient at transferring heat. For example, their effective thermal conductivity is several orders of magnitude higher than that of solid copper.
  • the number, length, diameter, shape, working fluid, and other performance parameters of the heat pipes are selected based on the desired degree of heat transfer during engine operation. The operation of the heat pipes 28 are described in more detail below.
  • the characteristics of the heat pipes 28, especially their forward sections 32 may be varied to accommodate their individual orientation.
  • a heat pipe 28 with a substantially horizontal forward section 32, or a heat pipe 28 with a vertical forward section 32 extending upwardly may require a design providing stronger capillary action to ensure adequate condensate return, than a heat pipe 28 with its forward section 32 extending downwardly.
  • oil which has absorbed heat from various parts of the engine is circulated into the heat exchanger where it heats the hot or evaporator ends of the heat pipes 28.
  • the working fluid within the heat pipes 28 absorbs that heat and evaporates.
  • the vapor generated then travels through the cavities, and condenses at the cold portions or ends of the heat pipes 28, thereby transferring heat to the cold portions or ends.
  • a wick or other capillary structure that extends from one end of the heat pipe 28 to the other transports the condensed liquid back to the hot portions or hot ends by capillary action, thereby completing the circuit.
  • the resultant heat transfer to the splitter 12 is effective to prevent ice formation (i.e. anti-icing) and/or remove ice which has formed on the splitter 12 (i.e. de-icing), depending on the heating rate.
  • the heat transfer system described herein being passive, needs no valves and is sealed.
  • the number, size, and location of the heat pipes 28 can be selected to provide heat removal and transfer as needed. Depending upon the exact configuration chosen, the system performance may be used only for anti-icing or for de-icing.
  • the heat transfer system makes use of heat which is undesired in one portion of an engine and uses that heat where it is need in another portion of the engine, avoiding both the losses associated with prior art cooling systems and the need for a separate anti-icing heat source.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Combustion & Propulsion (AREA)
  • Chemical & Material Sciences (AREA)
  • Thermal Sciences (AREA)
  • Life Sciences & Earth Sciences (AREA)
  • Physics & Mathematics (AREA)
  • Sustainable Development (AREA)
  • Heat-Exchange Devices With Radiators And Conduit Assemblies (AREA)
  • Exhaust Silencers (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP07123431.4A 2006-12-27 2007-12-18 Wärmeübertragungssystem für Turbinenmotoren mit Wärmerohren Expired - Fee Related EP1942249B1 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US11/616,555 US8015788B2 (en) 2006-12-27 2006-12-27 Heat transfer system for turbine engine using heat pipes

Publications (3)

Publication Number Publication Date
EP1942249A2 true EP1942249A2 (de) 2008-07-09
EP1942249A3 EP1942249A3 (de) 2014-03-05
EP1942249B1 EP1942249B1 (de) 2015-10-28

Family

ID=39266414

Family Applications (1)

Application Number Title Priority Date Filing Date
EP07123431.4A Expired - Fee Related EP1942249B1 (de) 2006-12-27 2007-12-18 Wärmeübertragungssystem für Turbinenmotoren mit Wärmerohren

Country Status (6)

Country Link
US (1) US8015788B2 (de)
EP (1) EP1942249B1 (de)
JP (1) JP5227013B2 (de)
CN (2) CN101210518A (de)
CA (1) CA2614160C (de)
RU (1) RU2007149313A (de)

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2148045A1 (de) * 2008-07-25 2010-01-27 Siemens Aktiengesellschaft Gehäuseabschnitt für eine Gasturbine
EP2194233A3 (de) * 2008-12-05 2012-08-01 Rolls-Royce Deutschland Ltd & Co KG Strömungsteiler für ein Fantriebwerk
EP2740905A1 (de) 2012-12-07 2014-06-11 Techspace Aero S.A. Lipe einer Trennwand in einer axialen Turbomaschine mit Enteisungsvorrichtung, zugehörige Verdichter und Turbomaschine
EP2481893A3 (de) * 2011-01-31 2016-07-27 General Electric Company Erwärmter Verteilerkanal eines Boosters
GB2536751A (en) * 2015-02-25 2016-09-28 Rolls-Royce Controls And Data Services Ltd Icing prevention of a gas turbine engine pressure sensing assembly
BE1022957B1 (fr) * 2015-04-20 2016-10-21 Techspace Aero S.A. Bec de separation degivrant de compresseur de turbomachine axiale
EP3239479A1 (de) * 2016-04-28 2017-11-01 General Electric Company Fluidkühlsystem für ein gasturbinentriebwerk und zugehöriges gasturbinentriebwerk
US10472984B2 (en) 2016-09-12 2019-11-12 Rolls-Royce Plc Apparatus for insertion into a cavity of an object
EP3640139A1 (de) * 2018-10-19 2020-04-22 Airbus Operations (S.A.S.) Motorgondel eines luftfahrzeugs, die mit einem vereisungs-schutzsystem ausgestattet ist
EP3819218A1 (de) * 2019-11-05 2021-05-12 Rohr, Inc. Thermisches vereisungsschutzsystem mit nicht kreisförmigem pikkolorohr

Families Citing this family (44)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8534074B2 (en) 2008-05-13 2013-09-17 Rolls-Royce Corporation Dual clutch arrangement and method
US20100005810A1 (en) * 2008-07-11 2010-01-14 Rob Jarrell Power transmission among shafts in a turbine engine
US8480527B2 (en) 2008-08-27 2013-07-09 Rolls-Royce Corporation Gearing arrangement
US20100054926A1 (en) * 2008-08-29 2010-03-04 General Electric Company System and method for thermal management of a gas turbine inlet
US8075438B2 (en) 2008-12-11 2011-12-13 Rolls-Royce Corporation Apparatus and method for transmitting a rotary input into counter-rotating outputs
US8021267B2 (en) 2008-12-11 2011-09-20 Rolls-Royce Corporation Coupling assembly
DE102009055879A1 (de) * 2009-11-26 2011-06-01 Rolls-Royce Deutschland Ltd & Co Kg Flugzeugenteisungsvorrichtung und Triebwerksgondel einer Fluggasturbine mit Enteisungsvorrichtung
GB201101335D0 (en) * 2011-01-26 2011-03-09 Airbus Uk Ltd Aircraft slat assembly with anti-icing system
EP2586712B2 (de) * 2011-10-31 2018-02-14 Veltru AG Verfahren und Vorrichtung zum Einlegen von Produkten in Behälter in einer Roboterstrasse
US8988880B2 (en) 2012-09-19 2015-03-24 Ge Intelligent Platforms, Inc. Heat transfer assembly with heat pipe brace and method for assembling a heat transfer assembly
US9404392B2 (en) 2012-12-21 2016-08-02 Elwha Llc Heat engine system
US9752832B2 (en) 2012-12-21 2017-09-05 Elwha Llc Heat pipe
US9422063B2 (en) * 2013-05-31 2016-08-23 General Electric Company Cooled cooling air system for a gas turbine
US9963994B2 (en) 2014-04-08 2018-05-08 General Electric Company Method and apparatus for clearance control utilizing fuel heating
CN104121037B (zh) * 2014-07-18 2015-07-01 北京航空航天大学 热管涡轮盘
WO2016033071A1 (en) * 2014-08-25 2016-03-03 Sylvan Source, Inc. Heat capture, transfer and release for industrial applications
US9797310B2 (en) * 2015-04-02 2017-10-24 General Electric Company Heat pipe temperature management system for a turbomachine
US20160290230A1 (en) * 2015-04-02 2016-10-06 General Electric Company Heat pipe cooling system for a turbomachine
JP6585073B2 (ja) 2015-04-02 2019-10-02 ゼネラル・エレクトリック・カンパニイ ターボ機械におけるホイールおよびバケットのためのヒートパイプ温度管理システム
US20160290214A1 (en) * 2015-04-02 2016-10-06 General Electric Company Heat pipe cooled turbine casing system for clearance management
US20160290235A1 (en) * 2015-04-02 2016-10-06 General Electric Company Heat pipe temperature management system for a turbomachine
FR3047042B1 (fr) * 2016-01-22 2018-02-16 Safran Aircraft Engines Dispositif de degivrage d'un bec de separation et d'aubes directrices d'entree d'une turbomachine aeronautique
BE1023498B1 (fr) * 2015-10-07 2017-04-07 Safran Aero Boosters S.A. Bec anti givre de compresseur basse pression de turbomachine axiale
US20170184026A1 (en) * 2015-12-28 2017-06-29 General Electric Company System and method of soakback mitigation through passive cooling
US10309242B2 (en) * 2016-08-10 2019-06-04 General Electric Company Ceramic matrix composite component cooling
US10443497B2 (en) 2016-08-10 2019-10-15 Rolls-Royce Corporation Ice protection system for gas turbine engines
GB2553144B (en) * 2016-08-26 2019-10-30 Rolls Royce Plc Apparatus for insertion into a cavity of an object
SG11201901764RA (en) * 2016-09-01 2019-03-28 Additive Rocket Corp Structural heat exchanger
US10583933B2 (en) 2016-10-03 2020-03-10 General Electric Company Method and apparatus for undercowl flow diversion cooling
FR3062169B1 (fr) * 2017-01-20 2019-04-19 Safran Aircraft Engines Carter de module de turbomachine d'aeronef, comprenant un caloduc associe a un anneau d'etancheite entourant une roue mobile aubagee du module
US10450957B2 (en) * 2017-01-23 2019-10-22 United Technologies Corporation Gas turbine engine with heat pipe system
BE1024935B1 (fr) * 2017-01-26 2018-08-27 Safran Aero Boosters S.A. Compresseur avec virole interne segmentee pour turbomachine axiale
US10392968B2 (en) 2017-04-24 2019-08-27 United Technologies Corporation Turbine casing cooling structure
US10450892B2 (en) 2017-04-24 2019-10-22 United Technologies Corporation Thermal management of turbine casing using varying working mediums
FR3087419B1 (fr) * 2018-10-19 2020-10-30 Airbus Operations Sas Nacelle de moteur d’aeronef comprenant un systeme de protection contre le givre.
US11384687B2 (en) * 2019-04-04 2022-07-12 Pratt & Whitney Canada Corp. Anti-icing system for gas turbine engine
US11255264B2 (en) 2020-02-25 2022-02-22 General Electric Company Frame for a heat engine
US11326519B2 (en) 2020-02-25 2022-05-10 General Electric Company Frame for a heat engine
US11047306B1 (en) 2020-02-25 2021-06-29 General Electric Company Gas turbine engine reverse bleed for coking abatement
US11560843B2 (en) 2020-02-25 2023-01-24 General Electric Company Frame for a heat engine
CN111794862B (zh) * 2020-07-15 2021-10-22 山东大学 一种用于航空发动机进气口唇口的除冰装置及除冰方法
US11485499B2 (en) * 2020-10-13 2022-11-01 General Electric Company System and method for cooling aircraft components
FR3118906B1 (fr) * 2021-01-15 2023-06-09 Safran Turbomachine hybride a double flux pour aeronef, comprenant un generateur/moteur refroidi par caloducs
US11536198B2 (en) 2021-01-28 2022-12-27 General Electric Company Gas turbine engine cooling system control

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2136880A (en) * 1983-03-18 1984-09-26 Rolls Royce Anti-icing of gas turbine engine air intakes
US6079670A (en) * 1997-12-12 2000-06-27 Aerospatiale Societe Nationale Industrielle Hot air diffuser for a jet engine air inlet cowl with de-icing circuit
US20050050877A1 (en) * 2003-09-05 2005-03-10 Venkataramani Kattalaicheri Srinivasan Methods and apparatus for operating gas turbine engines

Family Cites Families (27)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4240257A (en) 1973-02-22 1980-12-23 The Singer Company Heat pipe turbo generator
US3917193A (en) * 1974-01-21 1975-11-04 Boeing Co Boundary layer control and anti-icing apparatus for an aircraft wing
US3965681A (en) 1975-06-30 1976-06-29 General Motors Corporation Internal combustion engine and turbosupercharger therefor with heat pipe for intake mixture heating
US4186559A (en) 1976-06-07 1980-02-05 Decker Bert J Heat pipe-turbine
GB1541894A (en) 1976-08-12 1979-03-14 Rolls Royce Gas turbine engines
GB1548836A (en) 1977-03-17 1979-07-18 Rolls Royce Gasturbine engine
GB1555587A (en) 1977-07-22 1979-11-14 Rolls Royce Aerofoil blade for a gas turbine engine
GB1605405A (en) 1977-07-22 1995-07-19 Rolls Royce Heat pipes
US5192186A (en) 1980-10-03 1993-03-09 Rolls-Royce Plc Gas turbine engine
GB2090333B (en) 1980-12-18 1984-04-26 Rolls Royce Gas turbine engine shroud/blade tip control
GB2245314B (en) 1983-05-26 1992-04-22 Rolls Royce Cooling of gas turbine engine shroud rings
US4688745A (en) * 1986-01-24 1987-08-25 Rohr Industries, Inc. Swirl anti-ice system
US5046920A (en) 1989-02-23 1991-09-10 Fuji Electric Co., Ltd. Bearing cooling system in horizontal shaft water turbine generator
US5228643A (en) * 1992-06-25 1993-07-20 Mcdonnell Douglas Corporation Energy-exchange system incorporating small-diameter tubes
DE59603548D1 (de) * 1995-08-29 1999-12-09 Zurecon Ag Zuerich Haltevorrichtung für Rohre
US5878808A (en) 1996-10-30 1999-03-09 Mcdonnell Douglas Rotating heat exchanger
US5964279A (en) 1997-02-10 1999-10-12 Fujikura Ltd. Cooler for electronic devices
US5975841A (en) 1997-10-03 1999-11-02 Thermal Corp. Heat pipe cooling for turbine stators
US5979220A (en) 1998-06-30 1999-11-09 Siemens Westinghouse Power Corporation In-situ sensors for gas turbines
US6841021B1 (en) * 2000-07-10 2005-01-11 General Electric Company Method of making a polyimide resin and carbon fiber molded tube clamp
US6725645B1 (en) * 2002-10-03 2004-04-27 General Electric Company Turbofan engine internal anti-ice device
JP4380138B2 (ja) * 2002-10-21 2009-12-09 日産自動車株式会社 車両用放熱装置
JP2005195223A (ja) * 2004-01-06 2005-07-21 Sekisui House Ltd 床下空間の熱を利用した室内空調装置
US7040389B2 (en) * 2004-05-12 2006-05-09 Hul-Chun Hsu Integrated heat dissipation apparatus
US20070234704A1 (en) * 2005-09-01 2007-10-11 General Electric Company Methods and apparatus for operating gas turbine engines
JP3125120U (ja) * 2006-06-28 2006-09-07 陳朝泉 発熱部材用ヒートシンク装置
US7823374B2 (en) * 2006-08-31 2010-11-02 General Electric Company Heat transfer system and method for turbine engine using heat pipes

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2136880A (en) * 1983-03-18 1984-09-26 Rolls Royce Anti-icing of gas turbine engine air intakes
US6079670A (en) * 1997-12-12 2000-06-27 Aerospatiale Societe Nationale Industrielle Hot air diffuser for a jet engine air inlet cowl with de-icing circuit
US20050050877A1 (en) * 2003-09-05 2005-03-10 Venkataramani Kattalaicheri Srinivasan Methods and apparatus for operating gas turbine engines

Cited By (18)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2148045A1 (de) * 2008-07-25 2010-01-27 Siemens Aktiengesellschaft Gehäuseabschnitt für eine Gasturbine
EP2194233A3 (de) * 2008-12-05 2012-08-01 Rolls-Royce Deutschland Ltd & Co KG Strömungsteiler für ein Fantriebwerk
US8438828B2 (en) 2008-12-05 2013-05-14 Rolls-Royce Deutschland Ltd & Co Kg Flow divider having breaking points for a fan engine
EP2481893A3 (de) * 2011-01-31 2016-07-27 General Electric Company Erwärmter Verteilerkanal eines Boosters
EP2740905A1 (de) 2012-12-07 2014-06-11 Techspace Aero S.A. Lipe einer Trennwand in einer axialen Turbomaschine mit Enteisungsvorrichtung, zugehörige Verdichter und Turbomaschine
US9869203B2 (en) 2012-12-07 2018-01-16 Safran Aero Boosters Sa Axial turbomachine blade with platforms having an angular profile
GB2536751B (en) * 2015-02-25 2017-07-19 Rolls Royce Plc Icing prevention of a gas turbine engine pressure sensing assembly
GB2536751A (en) * 2015-02-25 2016-09-28 Rolls-Royce Controls And Data Services Ltd Icing prevention of a gas turbine engine pressure sensing assembly
US10030536B2 (en) 2015-02-25 2018-07-24 Rolls-Royce Plc Icing prevention of a gas turbine engine pressure sensing assembly
EP3085925A1 (de) 2015-04-20 2016-10-26 Techspace Aero S.A. Enteisender trennungsschnabel eines kompressors einer axialen turbomaschine
BE1022957B1 (fr) * 2015-04-20 2016-10-21 Techspace Aero S.A. Bec de separation degivrant de compresseur de turbomachine axiale
EP3239479A1 (de) * 2016-04-28 2017-11-01 General Electric Company Fluidkühlsystem für ein gasturbinentriebwerk und zugehöriges gasturbinentriebwerk
CN107339158A (zh) * 2016-04-28 2017-11-10 通用电气公司 用于使用热管来热集成油储存器和出口导叶的系统和方法
US10472984B2 (en) 2016-09-12 2019-11-12 Rolls-Royce Plc Apparatus for insertion into a cavity of an object
EP3640139A1 (de) * 2018-10-19 2020-04-22 Airbus Operations (S.A.S.) Motorgondel eines luftfahrzeugs, die mit einem vereisungs-schutzsystem ausgestattet ist
FR3087420A1 (fr) * 2018-10-19 2020-04-24 Airbus Operations (S.A.S.) Nacelle de moteur d’aeronef comprenant un systeme de protection contre le givre.
US11518526B2 (en) 2018-10-19 2022-12-06 Airbus Operations Sas Aircraft engine nacelle comprising an anti-icing protection system
EP3819218A1 (de) * 2019-11-05 2021-05-12 Rohr, Inc. Thermisches vereisungsschutzsystem mit nicht kreisförmigem pikkolorohr

Also Published As

Publication number Publication date
JP2008163943A (ja) 2008-07-17
CN104747291A (zh) 2015-07-01
EP1942249A3 (de) 2014-03-05
US8015788B2 (en) 2011-09-13
CA2614160A1 (en) 2008-06-27
EP1942249B1 (de) 2015-10-28
CA2614160C (en) 2015-06-30
JP5227013B2 (ja) 2013-07-03
US20080159852A1 (en) 2008-07-03
RU2007149313A (ru) 2009-07-10
CN101210518A (zh) 2008-07-02

Similar Documents

Publication Publication Date Title
CA2614160C (en) Heat transfer system for turbine engine using heat pipes
EP1895123B1 (de) Turbineneinlassenteisungsvorrichtung und Kühlungvorrichtung eines Schmiermittels
EP1884628B1 (de) Wärmeübertragungssystem und -verfahren für Turbinenmotoren über Wärmerohre
RU2436975C2 (ru) Теплопередающая система для турбинного двигателя с использованием тепловых труб
EP1895124B1 (de) Ölkühlungsvorrichtung im Lüftergehäuse
US6990797B2 (en) Methods and apparatus for operating gas turbine engines
US20070234704A1 (en) Methods and apparatus for operating gas turbine engines
CA2509788A1 (en) Foreign object damage tolerant nacelle anti-icing system
EP3203039A1 (de) Kühlsystem für ein gasturbinentriebwerk, zugehöriges gasturbinentriebwerk und verfahren zur kühlung
CN117836508A (zh) 用于冷却飞行器的制冷剂且包括安全加热装置的系统以及使用这种系统的方法

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

AK Designated contracting states

Kind code of ref document: A2

Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HU IE IS IT LI LT LU LV MC MT NL PL PT RO SE SI SK TR

AX Request for extension of the european patent

Extension state: AL BA HR MK RS

PUAL Search report despatched

Free format text: ORIGINAL CODE: 0009013

AK Designated contracting states

Kind code of ref document: A3

Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HU IE IS IT LI LT LU LV MC MT NL PL PT RO SE SI SK TR

AX Request for extension of the european patent

Extension state: AL BA HR MK RS

RIC1 Information provided on ipc code assigned before grant

Ipc: F01D 5/04 20060101AFI20140128BHEP

Ipc: F01D 25/02 20060101ALI20140128BHEP

Ipc: F02C 7/047 20060101ALI20140128BHEP

Ipc: F01D 25/10 20060101ALI20140128BHEP

Ipc: F01D 25/08 20060101ALI20140128BHEP

Ipc: F01D 5/08 20060101ALI20140128BHEP

17P Request for examination filed

Effective date: 20140905

RBV Designated contracting states (corrected)

Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HU IE IS IT LI LT LU LV MC MT NL PL PT RO SE SI SK TR

AKX Designation fees paid

Designated state(s): DE FR GB

17Q First examination report despatched

Effective date: 20150109

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

INTG Intention to grant announced

Effective date: 20150630

RIN1 Information on inventor provided before grant (corrected)

Inventor name: STEPHENSON, JUSTIN P.

Inventor name: VENKATARAMANI, KATTALAICHERI SRINIVASAN

Inventor name: MONIZ, THOMAS ORY

GRAS Grant fee paid

Free format text: ORIGINAL CODE: EPIDOSNIGR3

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): DE FR GB

REG Reference to a national code

Ref country code: GB

Ref legal event code: FG4D

REG Reference to a national code

Ref country code: DE

Ref legal event code: R096

Ref document number: 602007043654

Country of ref document: DE

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 9

REG Reference to a national code

Ref country code: DE

Ref legal event code: R097

Ref document number: 602007043654

Country of ref document: DE

PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT

26N No opposition filed

Effective date: 20160729

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 10

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 11

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: DE

Payment date: 20191119

Year of fee payment: 13

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: FR

Payment date: 20191120

Year of fee payment: 13

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: GB

Payment date: 20191122

Year of fee payment: 13

REG Reference to a national code

Ref country code: DE

Ref legal event code: R119

Ref document number: 602007043654

Country of ref document: DE

GBPC Gb: european patent ceased through non-payment of renewal fee

Effective date: 20201218

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: FR

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20201231

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: DE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20210701

Ref country code: GB

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20201218